Air compressor system

ABSTRACT

A gas turbine driven air compressor system including a first compressor feeding a portion of its compressed air to the turbine for combustion purposes and a second positive displacement compressor receiving the remaining compressed air from the first compressor and boosting its pressure for use as compressed air.

O Unlted States Patent 1 51 3,640,646 Hornschuch et al. 1 Feb. 8, 1972 [54] AIR COMPRESSOR SYSTEM 1,927,799 9/1933 Mann ..417/203 [72] inventors: Hanns Hornschuch Eamon, Pa; William 2,741,422 4/1956 Kockritz et a1. .417/20 Alder-819 Bmkslde FOREIGN PATENTS 0R APPLICATIONS [731 Assign: lngemll'kand 912,054 7/1946 France 417/3s1 [22] Filed: Mar. 26, 1970 Primary Examiner-Robert M. Walker 1 1 p N01 22,982 Attorney-Frank S.Troid1, Bernard J. Murphy and David w.

Tibbott [52] U.S.Cl ..417/203,417/243,417/381 1 5 1 1 1111. C1 ..F04b 23/14, F04b 23/00, F04b 17/00 A RA [58] held of Search 12 A gas turbine driven air compressor system including a first I compressor feeding a portion of its compressed air to the turl56 References Cited bme for combustion purposes and a second POS1UV displacement compressor receiving the remaining compressed air UNITED STATES PATENTS from the first compressor and boosting its pressure for use as compressed air. 2,811,362 10/1957 Hodge et al ..417/409 X 2,628,015 2/1953 Neugebauer et al. ..417/243 X 3 Claims, 1 Drawing Figure FUEL Pmmsorw a ma 3.610.648

INVENTORS HA IVA .5 HOR/VSCHUGH W/L 1. MM 7: ALDERSO/V AGENT AIR COMPRFSSOR SYSTEM BACKGROUND OF INVENTION The present invention relates to an air compressor system utilizing a gas turbine as a prime mover or driver.

Conventional portable air compressors are driven by reciprocating internal combustion engines. In the larger portable compressors, say 1,000 c.f.m. or higher, the use of reciprocating engines makes the portable compressor relatively large and heavy. As a result, it is impractical today to build engine-driven portable compressors having a capacity of more than 1,200 c.f.m.

SUMMARY OF INVENTION The principal object of this invention is to provide a novel portable air compressor driven by a gas turbine.

Other important objects of this invention are; to provide a more efficient air compressor unit driven by a gas turbine; to provide an air compressor driven by a gas turbine in which part of the compressed air is used in the gas turbine; and to provide a gas turbine driven air compressor having a readily variable discharge pressure ranging from about 100 to 30 p.s.i.g.

In general, the foregoing objects are attained in an air compressor system including a first compressor driven by a gas turbine with a part of the air handled by the air compressor going to the gas turbine as combustion air. The remainder of the air from the first compressor is boosted by a second compressor of positive displacement design and driven by the gas turbine. The compressed air from the second compressor flows to a line for use as compressed air. Due to the use of the positive displacement compressor as the second compressor, the compressed air delivered from the system can be varied over a wide range of pressures, say 100 to 300 p.s.i.g.

BRIEF DESCRIPTION OF DRAWING The single FIGURE in the drawing is a schematic diagram of the novel gas turbine air compressor of this invention.

DESCRIPTION OF SPECIFIC EMBODIMENT The single figure in the drawing schematically discloses a drive shaft 1 driven by a two-stage turbine wheel 2 and driving a two-stage centrifugal compressor 3 and a positive displacement rotary compressor 4 of the screw type. Air is sucked into the inlet 5 of the two-stage centrifugal compressor 3, is compressed in the first stage, passes through an intercooler 7 and then through the second stage. The air exits from the second stage into an outlet line 8 which feeds it to a dividing valve 9. The dividing valve 9 divides the air into two parts, one part for use as combustion air in the gas turbine 2 and the other part for use as compressed air.

The combustion air exits from the valve 9 through a line 10 to an air heater 11 mounted in the exhaust line of the gas turbine 2 for recapturing some of the heat in the turbine exhaust gases and using it to heat the combustion air. The combustion air flows from the air heater 11 though a line 12 to the combustion chamber 14. The combustion air mixes with fuel in the combustion chamber with the resulting mixture being ignited and combusted before entering the turbine 2 where it expends a part of its energy by driving the turbine 2.

The other portion of the air in the dividing valve 9 which will be used as compressed air flows through a line 15 to an after cooler 16 where it is cooled before entering a line 17 feeding it to the positive displacement screw compressor 4. This air is boosted in pressure in the compressor 4 and is then fed through the line 19 to a compressed air receiver 20. The exit port of the receiver is connected to an air line 21 through a valve 22.

While a single embodiment of the invention is illustrated and described, it should be understood that this invention is not limited merely to the particular structure described in the specification and shown in the drawin but may include other embodiments and modifications utrrzing the concept an teachings of the invention.

I claim:

1. An air compressor system, comprising:

a first compressor having two stages for compression;

a second compressor;

a single gas turbine, drivingly coupled to said first and second compressors, and having a combustion chamber; single air inlet means for admitting air to said first and second compressors and to said gas turbine;

a first line interconnecting the discharge port of said first compressor to said combustion chamber of said gas turbine;

heat exchange means, interposed in said first line and in gas flow communication with the discharge port of said gas turbine;

a second line interconnecting said first line to the inlet port of said second compressor whereby a portion of the compressed air discharged by said first compressor is delivered to said second compressor;

a third line receiving compressed air from said second compressor for use in operating compressed air equipment; and

an intercooler located between said two stages of said first compressor.

2. The air compressor system of claim 1 including:

an intercooler located in said second line for cooling compressed air flowing through said second line.

3. The air compressor system of claim I wherein:

sad second compressor is a positive displacement type of compressor. 

1. An air compressor system, comprising: a first compressor having two stages for compression; a second compressor; a single gas turbine, drivingly coupled to said first and second compressors, and having a combustion chamber; single air inlet means for admitting air to said first and second compressors and to said gas turbine; a first line interconnecting the discharge port of said first compressor to said combustion chamber of said gas turbine; heat exchange means, interposed in said first line and in gas flow communication with the discharge port of said gas turbine; a second line interconnecting said first line to the inlet port of said second compressor whereby a portion of the compressed air discharged by said first compressor is delivered to said second compressor; a third line receiving compressed air from said second compressor for use in operating compressed air equipment; and an intercooler located between said two stages of said first compressor.
 2. The air compressor system of claim 1 including: an intercooler located in said second line for cooling compressed air flowing through said second line.
 3. The air compressor system of claim 1 wherein: said second compressor is a positive displacement type of compressor. 